Missile interference identification algorithm

Abstract

The invention discloses a missile interference identification algorithm, which belongs to the field of missile flight test data analysis, and comprises the following steps: 1, preprocessing angular velocity information acquired by an inertial measurement device, including unit transformation and high-frequency noise filtering; 2, selecting a proper time interval according to the processed angularvelocity information, and resolving angular acceleration information; 3, according to the angular acceleration information and the moment of inertia of the missile, solving the total moment componentof each axis under the missile system; 4, according to the Mach number, the synthetic attack angle, the airflow roll angle, the mass center, the rudder deflection angle and other information, solvingtorque components of all shafts under a missile system under the free flow of the missile; and 5, subtracting the moment flowing down freely from the total moment of each shaft under the projectile system to obtain a projectile disturbance moment component of each shaft under the projectile system. According to the missile interference identification algorithm, high-frequency signals are filteredout in a targeted mode, and phase lag is reduced as much as possible, and it is ensured that the processed angular velocity information can be used for extracting mechanical missile interference.

Description

technical field [0001] The invention relates to the field of airborne missile flight test data analysis, in particular to an airborne missile interference identification algorithm, in particular to an aerodynamic interference identification method for an airborne missile ejection separation section of an internal or external catapult launcher. Background technique [0002] In order to meet the diverse needs of combat aircraft hang points and the needs of stealth performance, the launch method of airborne missiles has developed from the traditional sliding rail type to the catapult type. Due to the short distance between the missile and the carrier aircraft, a strong interference force and interference torque will be generated between the missile and the carrier aircraft, forming a more complex flow field environment. Obtaining accurate missile jamming is particularly important for the safe ejection and separation of missiles. [0003] At present, the CTS test is mainly used...

AI Technical Summary

Problems solved by technology

[0004] The problem to be solved by the technology of the present invention is to use the angular velocity information containing high-frequency noise obtained from the flight test inertial measurement device, after data preprocessing, to identify aircraft-bullet interference, so as to obtain aircraft-bullet interference

Images